Accession Number : AD0772736
Title : Program to Improve the Fracture Toughness and Fatigue Resistance of Aluminum Sheet and Plate for Airframe Applications.
Descriptive Note : Final technical rept. 1 Jul 72-1 Jul 73,
Corporate Author : BOEING COMMERCIAL AIRPLANE CO SEATTLE WASH
Personal Author(s) : Hyatt,Michael V.
Report Date : SEP 1973
Pagination or Media Count : 108
Abstract : Mechanical, fracture, smooth and notched fatigue, fatigue crack growth rate, and exfoliation corrosion tests were conducted to evaluate the effects of the various thermomechanical treatments. For comparison purposes, data were obtained on the commercial alloys 2024-T3, 7075-T6, 7475-T61, 7475-T761. In addition, a few TMTs on the commercial 7475 alloy were evaluated. (Modified author abstract)
Descriptors : *Aluminum alloys, *Fracture(Mechanics), Fatigue(Mechanics), Thermomechanics, Toughness, Exfoliation, Crack propagation, Microstructure, Airframes
Subject Categories : Aircraft
Properties of Metals and Alloys
Distribution Statement : APPROVED FOR PUBLIC RELEASE